@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

MODIFICATION No.: None

This page transmits Revision No.01 of Service Bulletin No.A340-25-4351

ADDITIONAL WORK

**CONF ALL

No additional work is required by this revision for aircraft modified by any previous issue.

REASON

Revision No. 01 issued to:

- add Service Bulletin No A340-25-4354 as terminating solution,

- update the effectivity,

- and minor changes.

CHANGES

SUMMARY

REASON/DESCRIPTION/OPERATIONAL

CONSEQUENCES

REASON UPDATED R

MATERIAL PRICE INFORMATION MATERIAL PRICE INFORMATION TABLE

UPDATED

R

EFFECTIVITY OPERATOR LIST UPDATED R

PLANNING INFORMATION

EFFECTIVITY EFFECTIVITY RELATED INFORMATION

UPDATED

R

Configuration definition

CONF 001 CONFIGURATION DEFINITION UPDATED R

Material Effectivity MATERIAL EFFECTIVITY UPDATED

MATERIAL SET UPDATED

R

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 1

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

REASON

Objective/Action OBJECTIVE/ACTION UPDATED R

COMPLIANCE

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

Accomplishment Timescale ACCOMPLISHMENT TIMESCALE UPDATED

CONFIGURATION UPDATED

R

REFERENCES REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

REFERENCED DOCUMENTATION UPDATED R

MATERIAL INFORMATION

MATERIAL - PRICE AND AVAILABILITY

Procurement Addresses PROCUREMENT ADDRESSES UPDATED

MATERIAL SET UPDATED

R

LIST OF MATERIALS - OPERATOR

SUPPLIED

Components COMPONENTS UPDATED R

Component COMPA03 PART MATERIAL SET UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Component COMPA04 PART MATERIAL SET UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Component COMPA05 PART MATERIAL SET UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

R

Component COMPA07 PART MATERIAL SET DELETED D

ACCOMPLISHMENT INSTRUCTIONS

TASK 254351- 832-801-001-Inspection.

Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 2

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

Subtask 254351-700-001-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

REFERENCES UPDATED

R

Subtask 254351-700-004-001 SUBTASK SOLUTION UPDATED

REFERENCED DOCUMENTATION UPDATED

CONFIGURATION UPDATED

REFERENCES UPDATED

R

TASK 254351- 833-801-001-Replace

Bracket No. 6.

Subtask 254351-833-001-001 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 254351-833-001-002 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 254351-833-001-003 SUBTASK SOLUTION UPDATED

QUANTITY UPDATED

ITEM NUMBER UPDATED

PART NUMBER UPDATED

KEYWORD UPDATED

PART NUMBER DESCRIPTION UPDATED

MATERIAL LIST UPDATED

R

Subtask 254351-833-001-004 SUBTASK SOLUTION UPDATED R

TASK 254351- 833-802-001-Replace

Bracket No. 7.

Subtask 254351-833-002-001 SUBTASK SOLUTION UPDATED

ITEM NUMBER UPDATED

R

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 3

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@A340

SERVICE BULLETIN

REVISION TRANSMITTAL SHEET

Subtask 254351-833-002-002 SUBTASK SOLUTION UPDATED

ITEM NUMBER UPDATED

R

Subtask 254351-833-002-003 SUBTASK SOLUTION UPDATED

ITEM NUMBER UPDATED

R

Subtask 254351-833-002-004 SUBTASK SOLUTION UPDATED

ITEM NUMBER UPDATED

MATERIAL LIST UPDATED

R

Fig. A-FBBAA

Fig. A-FBBAA Sheet 02 SHEET UPDATED R

Fig. A-FBBAA Sheet 03 SHEET UPDATED R

Fig. A-FBBAC

Fig. A-FBBAC Sheet 02 SHEET UPDATED R

Fig. A-FBBAC Sheet 03 SHEET UPDATED R

Fig. A-FBBAD

Fig. A-FBBAD Sheet 02 SHEET UPDATED R

Fig. A-FBBAD Sheet 03 SHEET UPDATED R

Fig. A-FBDAA

Fig. A-FBDAA Sheet 02 SHEET UPDATED R

Fig. A-FBDAB

Fig. A-FBDAB Sheet 02 SHEET UPDATED R

Fig. A-FBDAC

Fig. A-FBDAC Sheet 02 SHEET UPDATED R

Fig. A-FFAAA

Fig. A-FFAAA Sheet 01 SHEET UPDATED R

FILLING INSTRUCTIONS

This Service Bulletin has been generated electronically and is reissued as a complete document.

Replace the complete document.

Put this Revision Transmittal Sheet in front of the Service Bulletin.

HISTORY OF PREVIOUS REVISIONS

No previous revision

REVISION SEQUENCE

ORIGINAL: Sep 10/13

REVISION No. : 01 - Jan 31/14

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 4

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@A340

SERVICE BULLETIN

SUMMARY

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

This summary is for information only and is not approved for modification of the aircraft.

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

**CONF ALL

MODIFICATIONS

None

REASON/DESCRIPTION/OPERATIONAL CONSEQUENCES

During flight tests carried out with A340-600, high stress level were measured on the bracket No. 6 (PN

F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000 Post Mod No. 55128S18242),

which is one of the 8 parts used to attach the cockpit instrument panel to the aircraft structure.

This is linked to a coupling between the vibration levels due to the bumps of the runways and

introduced through the Nose Landing Gear (NLG), and the cockpit panel. Using accelerations

introduced at pilot seat location, the bracket No. 6 cannot sustain any fatigue loads of the Long Range

Design Service Goal (DSG).

Accomplishment of this Inspection Service Bulletin is no longer necessary in the case of Service

Bulletin A340-25-4354 has been embodied.

This inspection Service Bulletin requires performing a detailed inspection before 17,200 Flight Cycles

(FC) of the bracket No. 6 PN F2511012820000 Pre Mod No. 55128S18242 or PN F2511373420000

Post Mod No. 55128S18242 of the Cockpit Instrument Panel.

Depending on the results of this inspection, this Service Bulletin is issued to give the relevant corrective

action.

Accomplishment of this Service Bulletin will prevent the risk of having the Bracket No. 6 fully broken

and, consequently, further damage on the surrounding structure.

GENERAL EVALUATION

EVALUATION TABLE

COMPLIANCE MANDATORY (1) CANCELS INSPECTION SB NO

POTENTIAL AD YES A/C OPERATION AFFECTED NO

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 1

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SERVICE BULLETIN

SUMMARY

EVALUATION TABLE

RELIABILITY AFFECTED NO PAX COMFORT AFFECTED NO

COST SAVING NO LROPS AFFECTED NO

STRUCTURAL LIFE EXTN NO VENDOR SB INVOLVED NO

NOTE (1): Service Bulletin must be accomplished.

MATERIAL PRICE INFORMATION

**CONF 001

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA03 1 See SB Fastening

Component COMPA08 1 See SB Fastening

**CONF 002

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA04 1 See SB Fastening

Component COMPA09 1 See SB Fastening

**CONF 003

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 2 See SB Bracket

Component COMPA05 1 See SB Fastening

Component COMPA10 1 See SB Fastening

**CONF 004

MATERIAL PRICE INFORMATION TABLE

MATERIAL SET QTY PER

A/C

PRICE PER

A/C (USD)

MAIN PARTS

Component COMPA01 1 See SB Bracket

Component COMPA02 1 See SB Bracket

Component COMPA06 1 See SB Fastening

Component COMPA10 1 See SB Fastening

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 2

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@A340

SERVICE BULLETIN

SUMMARY

EFFECTIVITY

**CONF ALL

This Service Bulletin is applicable to this (these) operator(s) :

15R 15T 56W 58X 83V ABD ABQ AFR AIB ALK ARG CAL CCA

CPA DGA DLH FIN GAF GFA HFY IBE IRC IRM KAC LAN M3R

MAU MDG MSR NMB OAL PAL QAF RJA S3R SAA SAS SFB SLM

SVW SWR TAP THT THY UAE VCV VIR XAX

CONCURRENT REQUIREMENTS

None

REFERENCES / REPERCUSSIONS

TFU None

OEB None

AOT None

SIL None

LINE MAINTENANCE AFFECTED No

LIFE LIMIT None

OTHER None

NATURE OF THE WORK

AIRCRAFT YES

EQUIPMENT NO

HARD NO

SOFT NO

OBRM NO

MANPOWER

**CONF 001

Task 254351-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 3

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@A340

SERVICE BULLETIN

SUMMARY

**CONF 002

Task 254351-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Task 254351-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Task 254351-832-801-001: Inspection.

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

APPENDICES

**CONF ALL

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 4

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@A340

SERVICE BULLETIN

SUMMARY

**CONF ALL

TO BE INSPECTED

A

A

TO BE INSPECTED

BRACKET No 6

BRACKET No 7

F_SB_254351_5_SAAA_01_01

Figure A-FSAAA - Sheet 01

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 5

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@A340

SERVICE BULLETIN

SUMMARY

This Page Intentionally Left Blank

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 6

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@A340

SERVICE BULLETIN

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX

FRANCE

Tel : (33) 5 61 93 33 33

Telex : AIRBU 530526F

Fax : (33) 5 61 93 42 51

MANDATORY MANDATORY MANDATORY

ATA SYSTEM: 25

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

MODIFICATION No.: None

This document contains AIRBUS PROPRIETARY INFORMATION and shall at all times remain the

property of AIRBUS; no intellectual property right or licence is granted by AIRBUS in connection with

any information contained in it. It is delivered on the express condition that said document and the

information contained in it shall be treated as confidential, shall not be used for any purpose other than

that for which it is hereby delivered. It shall not be disclosed in whole or in part to third parties and shall

not be duplicated in any manner (except for the purposes of performing the tasks described hereunder

and provided that any recipient of such document shall comply with the conditions herein), without

AIRBUS prior written consent.

1. PLANNING INFORMATION

**CONF ALL

A. EFFECTIVITY

(1) Models

340-211 340-212 340-213 340-311 340-312 340-313

(2) Effectivity by MSN

0002 0004 0006 0009 0011 0013-0014 0018-0020 0022-0029 0031-0035 0038 0041

0043-0044 0046-0049 0051-0053 0056-0058 0061 0063 0074-0076 0078-0081

0084-0085 0088-0091 0093-0094 0101 0104 0114-0115 0117 0123 0125-0126 0128

0131 0133-0137 0139 0141-0142 0145-0147 0149-0152 0154 0156-0161 0163-0164

0166-0170 0173-0176 0178-0180 0182 0185-0187 0190 0192-0194 0196-0197 0199

0201-0202 0204 0207-0208 0210 0212-0218 0220-0221 0225 0227-0228 0233

0236-0237 0242-0243 0245-0246 0252 0257 0260 0263-0264 0268 0270 0273-0274

0278 0280 0282 0292 0297 0302 0304 0307 0310 0318-0319 0321 0325 0327 0329

0331-0332 0335 0347 0352 0354-0355 0359 0363 0367 0373-0374 0377-0379 0381

0385 0387 0390 0395 0399 0402 0406 0411 0413-0415 0424 0429-0430 0433-0435

0438 0442 0446-0447 0450 0459 0467 0470 0474 0483 0528 0538 0541 0544-0546

0554 0556 0559 0561-0562 0582 0585 0590 0598 0643 0646 0651 0668 0793 0800

0835 0844 0921 0938 0955

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 1

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@A340

SERVICE BULLETIN

(3) Effectivity by Operator

The Operator/MSN relationship is provided for information only and is correct at the time

of issue in accordance with the information available to AIRBUS. Any future changes

resulting from transfer of an aircraft from one operator to another will not be reflected in

this list unless the Service Bulletin is revised for another reason.

OPERATOR MSN

15R 0151

15T 0009

56W 0011 0013 0018 0019

58X 0004

83V 0133

ABD 0210

ABQ 0216 0257

AFR 0029 0078 0084 0186 0207 0237 0245 0246 0260 0307 0310 0377

0399

AIB 0131 0141 0161 0182

ALK 0032 0033 0034 0367 0374 0381

ARG 0048 0063 0074 0080 0085 0093 0094 0123 0126 0128 0170 0193

0373

CAL 0402 0406 0411 0415 0433 0541

CCA 0192 0199 0201 0242 0243 0264

CPA 0136 0137 0142 0147 0157 0160 0208 0218 0220 0227 0228

DGA 0075 0081

DLH 0024 0027 0028 0035 0052 0053 0135 0158 0213 0233 0252 0297

0304 0321 0325 0327 0335 0347 0352 0354 0379 0390 0434 0447

FIN 0058 0168 0174 0835 0844 0921 0938

GAF 0274 0355

GFA 0212 0215 0282 0554

HFY 0117 0190 0202

IBE 0088 0125 0134 0145 0146 0217 0221 0329 0414 0459 0474 0483

IRC 0002

IRM 0020 0056

KAC 0089 0090 0101 0104

LAN 0359 0363 0429 0442

M3R 0061

MAU 0076 0152 0194 0268 0793 0800

MDG 0319

MSR 0156 0159 0178

NMB 0047 0051

OAL 0280 0292

PAL 0173 0176 0187 0196 0302 0318 0332 0387

QAF 0026 0528

RJA 0014 0022 0038 0043

S3R 0204

SAA 0006 0197 0378 0544 0582 0590 0643 0646 0651

SAS 0167 0413 0424 0430 0435 0450 0467 0470

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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@A340

SERVICE BULLETIN

OPERATOR MSN

SFB 0046

SLM 0049

SVW 0955

SWR 0150 0154 0169 0175 0179 0263 0538 0545 0546 0556 0559 0561

0562 0585 0598

TAP 0041 0044 0079 0091

THT 0385 0395 0438 0446 0668

THY 0023 0025 0057 0115 0180 0270 0331

UAE 0139 0149 0163 0166 0185 0236

VCV 0031

VIR 0114 0164 0214 0225

XAX 0273 0278

(4) Configuration by MSN

MSN CONFIGURATION

0002 0004 0006 0009 0011 0013 0014 0018 0019 0020 0022

0023 0024 0025 0026 0027 0028 0029 0031 0032 0033 0034

0035 0038 0041 0043 0044 0046 0047 0048 0049 0051 0052

0053 0056 0057 0058 0061 0063 0074 0075 0076 0078 0079

0080 0081 0084 0085 0088 0089 0090 0091 0093 0094 0101

0104 0114 0115 0117 0123 0125 0126 0128 0131 0133 0134

0135 0136 0137 0139 0141 0142 0145 0146 0147 0149 0150

0151 0152 0154 0156 0157 0158 0159 0160 0161 0163 0164

0166 0167 0168 0169 0170 0173 0174 0175 0176 0178 0179

0180 0182 0185

001

0186 0187 0190 0192 0193 0194 0196 0197 0199 0201 0202

0204 0207 0208 0210 0212 0213 0214 0215 0216 0217 0218

0220 0221 0225 0227 0228 0233 0236 0237 0242 0243 0245

0246 0252 0257 0260 0263 0264 0268 0270 0273 0274 0278

0280 0282 0292 0297 0302 0304 0307 0310 0318 0319 0321

0325 0327 0329 0331 0332 0335 0347 0352 0354 0355 0359

0363 0367 0373 0374 0377 0378 0379 0381 0385 0387 0390

0395 0399 0402 0406 0411 0413 0414 0415 0424 0429 0430

0433 0434 0435 0438 0442 0446 0447 0450 0459 0467 0470

0474 0483 0528 0538 0541 0544 0545 0546 0554 0556 0559

0561 0562 0582 0585 0590 0598 0643 0646 0651

002

0668 0793 0800 0835 0844 003

0921 0938 0955 004

(5) Configuration definition

**CONF 001

Config. 001 is valid for aircraft on which Mod. No. 45411S13604 , Mod. No.

53446S18217 and Mod. No. 55128S18242 are not embodied.

**CONF 002

Config. 002 is valid for aircraft on which Mod. No. 45411S13604 is embodied and Mod.

No. 53446S18217 and Mod. No. 55128S18242 are not embodied.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

**CONF 003

Config. 003 is valid for aircraft on which Mod. No. 45411S13604 and Mod. No.

53446S18217 are embodied and Mod. No. 55128S18242 is not embodied.

**CONF 004

Config. 004 is valid for aircraft on which Mod. No. 45411S13604 , Mod. No.

53446S18217 and Mod. No. 55128S18242 are embodied.

(6) Material Effectivity

**CONF 001

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA03 1

Consumable CMLA01 1

Component COMPA08 1

**CONF 002

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA04 1

Consumable CMLA01 1

Component COMPA09 1

**CONF 003

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 2

Component COMPA05 1

Consumable CMLA01 1

Component COMPA10 1

**CONF 004

MATERIAL QTY PER A/C SEE NOTES

Component COMPA01 1

Component COMPA02 1

Component COMPA06 1

Consumable CMLA01 1

Component COMPA10 1

**CONF ALL

B. CONCURRENT REQUIREMENTS

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 4

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@A340

SERVICE BULLETIN

C. REASON

(1) History

During flight tests carried out with A340-600, high stress level were measured

on the bracket No. 6 (PN F2511012820000 Pre Mod No. 55128S18242 or PN

F2511373420000 Post Mod No. 55128S18242), which is one of the 8 parts used to

attach the cockpit instrument panel to the aircraft structure.

This is linked to a coupling between the vibration levels due to the bumps of the

runways and introduced through the Nose Landing Gear (NLG), and the cockpit panel.

Using accelerations introduced at pilot seat location, the bracket No. 6 cannot sustain

any fatigue loads of the Long Range Design Service Goal (DSG).

(2) Objective/Action

Accomplishment of this Inspection Service Bulletin is no longer necessary in the case of

Service Bulletin A340-25-4354 has been embodied.

This inspection Service Bulletin requires performing a detailed inspection before 17,200

Flight Cycles (FC) of the bracket No. 6 PN F2511012820000 Pre Mod No. 55128S18242

or PN F2511373420000 Post Mod No. 55128S18242 of the Cockpit Instrument Panel.

Depending on the results of this inspection, this Service Bulletin is issued to give the

relevant corrective action.

(3) Advantages

Accomplishment of this Service Bulletin will prevent the risk of having the Bracket No. 6

fully broken and, consequently, further damage on the surrounding structure.

(4) Operational/Maintenance Consequences

None

D. DESCRIPTION

To accomplish this Service Bulletin it is necessary to :

**CONF 001

Task 254351-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 254351-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 5

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SERVICE BULLETIN

Task 254351-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7

(2) Install/Close Items Removed/Opened for access

**CONF 002

Task 254351-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 254351-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access

Task 254351-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7

(2) Install/Close Items Removed/Opened for access

**CONF 003

Task 254351-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 254351-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access

Task 254351-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7

(2) Install/Close Items Removed/Opened for access

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 6

5

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@A340

SERVICE BULLETIN

**CONF 004

Task 254351-832-801-001: Inspection.

(1) Do a Detailed Inspection of the Bracket No. 6.

(2) Do a Detailed Inspection of the Bracket No. 7.

(3) Install/Close Items Removed/Opened for access.

Task 254351-833-801-001: Replace Bracket No. 6.

(1) Replace the Bracket No. 6.

(2) Install/Close Items Removed/Opened for access

Task 254351-833-802-001: Replace Bracket No. 7.

(1) Replace the Bracket No. 7

(2) Install/Close Items Removed/Opened for access

**CONF ALL

E. COMPLIANCE

(1) Classification

MANDATORY: Service Bulletin must be accomplished.

(2) Accomplishment Timescale

**CONF 001

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

254351-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 7

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 254351-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 8

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 254351-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

254351-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF 002

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

254351-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 9

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 254351-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 10

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 254351-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

254351-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF 003

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

254351-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 11

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 254351-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 12

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 254351-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

254351-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF 004

This Service Bulletin has been classified Mandatory by the issue of an Airworthiness

Directive (AD) published by the European Aviation Safety Agency (EASA). The AD must

be used as the reference document for the mandated accomplishment timescale.

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

All aircraft Do a detailed inspection of the

bracket No. 6 (Refer to TASK

254351-832-801 001

Inspection. )

17,200 FC from

aircraft first flight

500 FC

See Note*

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 13

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

None None 2,600 FC

OR

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2600 FC None None

OR

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

No crack found

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. )

Within 2,600 FC

after inspection

None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Crack found and

both bracket lugs

are not fully broken

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

2,600 FC None None

Crack found and

both bracket lugs

fully broken

Do a detailed inspection of the

bracket No. 7 (Refer to

SUBTASK 254351-700-004

001 Do a Detailed Inspection

of the Bracket No. 7. )

Before next flight None None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 14

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Compliance (whichever occurs

later)

Condition Action

Threshold Grace period

from SB first

issuance date

Repetitive

interval

Replace the bracket No. 6

(Refer to TASK

254351-833-801 001 Replace

Bracket No. 6. ) and replace

the bracket No. 7 (Refer to

TASK 254351-833-802 001

Replace Bracket No. 7. )

Before next flight None None

AND

Do a detailed inspection of the

bracket No. 6 again (Refer to

TASK 254351-832-801 001

Inspection. )

17,200 FC None None

OR

Replace the bracket No. 7

(Refer to TASK

254351-833-802 001 Replace

Bracket No. 7. )

Before next flight None None

AND

No crack found on

bracket No. 7

Implement Service Bulletin

No. A340-25-4354 as

terminative solution.

Before next flight None None

Crack found on

bracket No. 7

Contact AIRBUS Before next flight None None

Note*: For AC having accumulated near or more than 17200 FC, perform the inspection before 500

FC from SB first issuance date

Table 1 - Do a detailed inspection of the Bracket No. 6.

**CONF ALL

F. APPROVAL

The technical content of this document is approved under the authority of Design

Organization Approval No. EASA.21J.031.

If an aircraft listed in the effectivity has a modification or repair embodied that is not of

AIRBUS origin, and which affects the content of this Service Bulletin, the operator is

responsible for obtaining approval by its airworthiness authority for any adaptation necessary

before incorporation of the Service Bulletin.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 15

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

G. MANPOWER

The manpower estimates given in this Service Bulletin are based on the direct labor cost to

do the work. These estimates assume that the work will be done by experienced personnel,

and may need to be revised upwards to suit operator’s circumstances. The estimates do not

include the time to prepare, plan or inspect the work. Manufacture and procurement of parts

and tools, drying times for paints, sealants, etc., and general administration work are also not

included.

**CONF 001

Task 254351-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Task 254351-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 16

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 254351-832-801-001: Inspection.

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Task 254351-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 17

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 254351-833-801-001: Replace Bracket No. 6.

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Task 254351-832-801-001: Inspection.

Get Access 2.50

On Aircraft

Do a Detailed Inspection of the Bracket No. 6. 1.00

Do a Detailed Inspection of the Bracket No. 7. 1.00

Install/Close Items Removed/Opened for access. 0.50

Close-Up 2.50

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

Task 254351-833-801-001: Replace Bracket No. 6.

Get Access 2.50

On Aircraft

Replace the Bracket No. 6. 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

Task 254351-833-802-001: Replace Bracket No. 7.

Get Access 2.50

On Aircraft

Replace the Bracket No. 7 2.00

Install/Close Items Removed/Opened for access 0.50

Tests 4.00

Close-Up 2.50

TOTAL MANHOURS 11.50

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 18

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Task 254351-833-802-001: Replace Bracket No. 7.

ELAPSED TIME (HOURS) 11.50

**CONF ALL

H. WEIGHT AND BALANCE

Not Changed

I. ELECTRICAL LOAD DATA

Not Changed

J. REFERENCES

**CONF 001

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A340-25-4354

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 002

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A340-25-4354

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 003

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A340-25-4354

Standards Manual (SM)

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 19

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF 004

Aircraft Maintenance Manual (AMM) 06-20-00 06-41-52 12-34-24

21-26-00 22-96-00 22-97-00

24-41-00 25-11-51 31-50-00

31-60-00 31-63-22 33-12-13

33-13-00 33-14-00 52-10-00

Elec. Std. Practices Manual (ESPM) 20-52-20 20-55-00

Service Bulletin (SB) A340-25-4354

Standards Manual (SM)

Structural Repair Manual (SRM) 51-24-00 51-42-00 51-43-00

51-44-00 51-75-12

**CONF ALL

K. PUBLICATION AFFECTED

Illustrated Parts Catalog (IPC) 25-14-01

Impact on Scheduled maintenance: Refer to MPD

L. INTERCHANGEABILITY/MIXABILITY

Not Applicable

M. SPARES

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 20

5

Printed in FRANCE © AIRBUS S.A.S. 2007. All rights reserved.
@A340

SERVICE BULLETIN

2. MATERIAL INFORMATION

**CONF ALL

A. MATERIAL - PRICE AND AVAILABILITY

(1) Procurement Addresses

Customers with aircraft shown in the effectivity of this Service Bulletin should send a

purchase order to AIRBUS. Quote the number of this Service Bulletin. The address is:

Component COMPA01

Component COMPA02

AIRBUS

Material, Logistic and Supplier IFD - In Flight

Desk

Weg beim Jaeger 150

D-22335 HAMBURG

GERMANY

For ordering by internet:

http://spares.airbus.com

For ordering by fax: +49 40 50 76 4012

For ordering by E-mail:

ifd.spares@airbus.com

AIRBUS Material, Logistics and Suppliers do not stock standard hardware as competitive

multiple suppliers ensure access to minimum prices AIRBUS recommends Customers

with aircraft shown in the effectivity of this Service Bulletin to send a purchase order to

B/E Aerospace. The address is:

Component COMPA03

Component COMPA04

Component COMPA05

Component COMPA06

Component COMPA08

Component COMPA09

Component COMPA10

B/E AEROSPACE INC.

CONSUMABLES MANAGEMENT

10000 NW 15th Terrace Miami

FL 33172

Tel EMEA: +49 (0) 40 822 285 31500

Tel US: +1 305 925 2600

Tel ASIA: +1 310 900 1300

Fax EMEA: +49 (0) 40 822 285 31010

Fax US: +1 305 507 7191

Fax ASIA: +1 310 819 1200

SITA: MIAMMCR

E-Mail: AOGdesk_CMG@beaerospace.com

internet: http://www.beconsumables.com

or, alternatively any other source on the open

market

(2) Price and Availability

No AIRBUS kit will be provided.

Operator supplied AIRBUS parts required to accomplish this Service Bulletin are to be

purchased by a spares purchase order.

Operator supplied standard hardware parts required to accomplish this Service Bulletin

are to be supplied from the Operator’s stock.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 21

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SERVICE BULLETIN

B. INDUSTRY SUPPORT INFORMATION

AIRBUS will not provide industry support for accomplishment of this Service Bulletin.

C. LIST OF COMPONENTS

No Kit

D. LIST OF MATERIALS - OPERATOR SUPPLIED

(1) Consumable Materials

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO CML

MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base GreaseGeneral Purpose Low T03HBD9 As required

(2) Components

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

16 F2511012820095 1 BRACKET (16) F2511012820000

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

6 F2511373420095 1 BRACKET (6) F2511373420000

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA06

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

9 EN6115V3-5 4 BOLT

10 ASNA2531-3 4 NUT

11 ASNA2050DCJ3215 3 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 23

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

21 MS24665-71 1 PIN

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA08

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

15 ASNA2050DEJ4020 4 RIVET

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA09

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA10

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 2 BOLT

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD ITEM OLD PART N ̊ INT SEE

NOTES

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: If you find part numbers of hardware components in the related kit(s)

which you cannot identify in the LIST OF COMPONENTS of this Service

Bulletin, refer to Standards Manual (SM). The SM will give you the

correct part number to part number relationship.

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

(3) Equipment

None

E. PARTS TO BE RE-IDENTIFIED BY OPERATOR

None

F. TOOLING

None

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 25

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This Page Intentionally Left Blank

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

3. ACCOMPLISHMENT INSTRUCTIONS

Task 254351-832-801-001 - Inspection.

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

NOTE: The purpose of flow charts is to supplement the information given in the Procedure

and Compliance paragraphs and not to serve as the primary source for tasks or

compliance times given in this Service Bulletin.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 27

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SERVICE BULLETIN

Task Associated Data

**CONF 001

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF 002

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF 003

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF 004

Zone

212

Manpower

TOTAL MANHOURS 7.50

ELAPSED TIME (HOURS) 7.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 254351-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 254351-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 254351-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 254351-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 254351-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 254351-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 29

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SERVICE BULLETIN

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 004

(1) Subtask 254351-910-001-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

(a) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(b) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(2) Subtask 254351-839-001-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 254351-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position at the door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(2) Subtask 254351-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF 002

(1) Subtask 254351-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 31

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position at the door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(2) Subtask 254351-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

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SERVICE BULLETIN

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF 003

(1) Subtask 254351-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position at the door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(2) Subtask 254351-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 33

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SERVICE BULLETIN

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF 004

(1) Subtask 254351-941-001-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position at the door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(2) Subtask 254351-010-001-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

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SERVICE BULLETIN

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

or

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

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2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 254351-700-004 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

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1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report, refer to Fig. A-FRAAA.

(3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 002

(1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 39

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@A340

SERVICE BULLETIN

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

or

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 254351-700-004 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 40

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@A340

SERVICE BULLETIN

(2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 41

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@A340

SERVICE BULLETIN

Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report, refer to Fig. A-FRAAA.

(3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 42

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@A340

SERVICE BULLETIN

**CONF 003

(1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

or

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 43

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@A340

SERVICE BULLETIN

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 254351-700-004 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

(2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 44

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@A340

SERVICE BULLETIN

Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report, refer to Fig. A-FRAAA.

(3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 45

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@A340

SERVICE BULLETIN

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 004

(1) Subtask 254351-700-001-001 - Do a Detailed Inspection of the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills AIRFRAME

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 6.

Refer to Fig. A-FBAAA

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 46

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@A340

SERVICE BULLETIN

Refer to Fig. A-FFAAA

1 If no crack is found:

a Do a detailed inspection of the bracket No. 6 at the interval given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

or

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

or

c Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

2 If a crack is found and both bracket lugs are not fully broken:

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

3 If a crack is found and both bracket lugs are fully broken:

a Do a detailed inspection of the bracket No. 7.

Refer to SUBTASK 254351-700-004 001

(b) Send inspection report to Airbus, refer to Fig. A-FRAAA.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 47

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@A340

SERVICE BULLETIN

(2) Subtask 254351-700-004-001 - Do a Detailed Inspection of the Bracket No. 7.

Manpower Resources

Manhours 1.00

Minimum number of person 1

Subtask elapsed time 1.00

Skills NON SPECIFIC

References

Service Bulletin (SB) A340-25-4354

Fig. A-FBAAA

Area to be inspected

Sheet 01

Sheet 02

Fig. A-FFAAA

Flow-chart

Sheet 01

Fig. A-FRAAA

Inspection Report

Sheet 01

At the threshold given in the PLANNING INFORMATION paragraph E.(2):

(a) Do a detailed inspection of the bracket No. 7.

Refer to Fig. A-FBAAA

Refer to Fig. A-FFAAA

1 If no crack is found on the bracket No. 7.

a Replace the bracket No. 6 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-801 001

Replace Bracket No. 6.

and

Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

Do a detailed inspection of the bracket No. 6 at the threshold given

in the PLANNING INFORMATION paragraph E.(2), refer to TASK

254351-832-801 001 Inspection.

OR

b Replace the bracket No. 7 at the threshold given in the PLANNING

INFORMATION paragraph E.(2), refer to TASK 254351-833-802 001

Replace Bracket No. 7.

and

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 48

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@A340

SERVICE BULLETIN

Implement Service Bulletin No. A340-25-4354 as terminative solution at

the threshold given in the PLANNING INFORMATION paragraph E.(2).

2 If a crack is found on the bracket No. 7.

a Contact AIRBUS before next flight.

(b) Send inspection report, refer to Fig. A-FRAAA.

(3) Subtask 254351-410-002-001 - Install/Close Items Removed/Opened for access.

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(b) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 49

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@A340

SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

None

**CONF 002

None

**CONF 003

None

**CONF 004

None

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 254351-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(c) Remove the access platform.

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 002

(1) Subtask 254351-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 50

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@A340

SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(c) Remove the access platform.

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 003

(1) Subtask 254351-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(c) Remove the access platform.

(d) Restore the systems and the aircraft to normal operation conditions.

**CONF 004

(1) Subtask 254351-942-001-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 51

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@A340

SERVICE BULLETIN

(c) Remove the access platform.

(d) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 52

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@A340

SERVICE BULLETIN

Task 254351-833-801-001 - Replace Bracket No. 6.

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 53

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@A340

SERVICE BULLETIN

Task Associated Data

**CONF 001

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 254351-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 54

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@A340

SERVICE BULLETIN

References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 254351-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 254351-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 55

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SERVICE BULLETIN

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 254351-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 254351-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 254351-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 004

(1) Subtask 254351-910-002-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 57

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SERVICE BULLETIN

(2) Subtask 254351-839-002-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 254351-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 59

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SERVICE BULLETIN

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 002

(1) Subtask 254351-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 003

(1) Subtask 254351-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

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(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 64

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**CONF 004

(1) Subtask 254351-941-002-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit (DU)

(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel 235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-002-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 254351-833-001-001 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA03

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 67

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAA

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAA

In accordance with SRM 51-42-00

1 Remove:

1 Screw Item (7) Discard

1 Nut Item (8) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

2 Rivet Item (15) Discard

2 Rivet Item (14) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAA

In accordance with SRM 51-42-00 and SRM 51-44-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 7.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NAS6604-10 Item 7

NOTE: Install the bolt item 7 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBBAA Sheet 04

a Check that the minimum clearances are 0.35 mm (0.026 in) at LHS and

0.65 mm (0.014 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 8:

1 Nut NAS1726-4E Item 8

NOTE: Torque the nut item 8 to a torque value between 0.28 and 0.37

mdaN (24.782 and 32.748 lbf.in).

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

(2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 002

(1) Subtask 254351-833-001-002 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA04

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 ASNA2050DCJ3215 3 RIVET

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAC

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAC

In accordance with SRM 51-42-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (20) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

2 Rivet Item (15) Discard

2 Rivet Item (14) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAC

In accordance with SRM 51-42-00 and SRM 51-44-00

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

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1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBBAC Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-134 Item 20

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 003

(1) Subtask 254351-833-001-003 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA05

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

11 ASNA2050DCJ3215 3 RIVET

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBBAD

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAD

In accordance with SRM 51-42-00

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

2 Rivet Item (15) Discard

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

2 Rivet Item (14) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAD

In accordance with SRM 51-42-00 and SRM 51-44-00

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBBAD Sheet 04.

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 77

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SERVICE BULLETIN

**CONF 004

(1) Subtask 254351-833-001-004 - Replace the Bracket No. 6.

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills AIRFRAME

Material necessary to do the job

Component COMPA02

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

6 F2511373420095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA06

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

9 EN6115V3-5 4 BOLT

10 ASNA2531-3 4 NUT

11 ASNA2050DCJ3215 3 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 78

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SERVICE BULLETIN

References

Fig. A-FBBAB

Replacement of the bracket No. 6

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 6.

Refer to Fig. A-FBBAB

In accordance with SRM 51-42-00

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the fasteners:

4 Bolt Item (9) Discard

4 Nut Item (10) Discard

3 Remove the bracket:

1 Bracket F2511373420000 Item (6) Discard

(b) Install the new bracket.

Refer to Fig. A-FBBAB

In accordance with SRM 51-42-00 and SRM 51-44-00

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a If necessary, remove:

3 Rivets Item (11) Discard

b Mark the position of the hole of the upper bracket on the new bracket.

c If removed, install:

3 Rivet ASNA2050DCJ3215 Item 11

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

3 Put in position the new bracket item 6 with the bolt item 17.

Install:

1 Bracket F2511373420095 Item 6

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 6 and the upper bracket

as shown in Fig. A-FBBAB Sheet 04.

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Bolt EN6115V3-5 Item 9

4 Nut ASNA2531-3 Item 10

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-003-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 80

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SERVICE BULLETIN

References

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 254351-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 81

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

**CONF 002

(1) Subtask 254351-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 84

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SERVICE BULLETIN

**CONF 003

(1) Subtask 254351-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 85

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1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

**CONF 004

(1) Subtask 254351-700-003-001 - Testing

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 86

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SERVICE BULLETIN

References

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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SERVICE BULLETIN

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 254351-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 88

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SERVICE BULLETIN

**CONF 002

(1) Subtask 254351-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

**CONF 003

(1) Subtask 254351-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

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(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

**CONF 004

(1) Subtask 254351-942-002-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish an associated Repair Task during the same

layover period, the subsequent Close-up procedure is not necessary.

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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Task 254351-833-802-001 - Replace Bracket No. 7.

**CONF ALL

WARNING: MAKE SURE THAT YOU OBEY ALL THE WARNINGS AND ALL THE CAUTIONS

INCLUDED IN THE REFERENCED PROCEDURES.

CAUTION: ALWAYS OBEY THE PRECAUTIONS THAT FOLLOW TO KEEP

ELECTRICAL WIRING IN A SATISFACTORY CONDITION (ELECTRICALLY

AND MECHANICALLY SERVICEABLE). WHEN YOU DO MAINTENANCE

WORK, REPAIRS OR MODIFICATIONS, ALWAYS KEEP ELECTRICAL WIRING,

COMPONENTS AND THE WORK AREA AS CLEAN AS POSSIBLE. TO DO

THIS:

- PUT PROTECTION, SUCH AS PLASTIC SHEETING, CLOTHS, ETC; AS

NECESSARY ON WIRING AND COMPONENTS.

- REGULARLY REMOVE ALL SHAVINGS, UNWANTED MATERIAL AND

OTHER CONTAMINATION.

THESE PRECAUTIONS WILL DECREASE THE RISK OF CONTAMINATION

AND DAMAGE TO THE ELECTRICAL WIRING INSTALLATION.

IN CASE OF CONTAMINATION REFER TO ESPM 20-55-00.

NOTE: The accomplishment instructions of this Service Bulletin refer to procedures

included in other AIRBUS documents. When the words "refer to" are used and the

operator has an accepted alternative procedure, the accepted alternative procedure

can be used. When the words "in accordance with" are included in the instruction,

the procedure in the AIRBUS document must be used.

NOTE: The access and close-up instructions, not comprising return to service tests, in this

Service Bulletin do not constitute or affect the technical intent of the Service

Bulletin. Operators can therefore, as deemed necessary, omit or add access and/or

close-up steps to add flexibility to their maintenance operations as long as the

technical intent of the Service Bulletin is met within the set parameters.

NOTE: Manual titles given in the accomplishment instructions are referred to by acronyms.

Refer to paragraph 1.J., References, for the definition of acronyms.

NOTE: This Service Bulletin is classified mandatory or expected to be classified mandatory

by an Airworthiness Directive (AD). The paragraphs 3.C. and 3.D. in these

accomplishment instructions are Required for Compliance (RC) and must be done

to comply with the AD. Other paragraphs are recommended and may be deviated

from, done as part of other actions or done with accepted methods different from

those given in the Service Bulletin, as long as the RC paragraphs can be done and

the aircraft can be put back into a serviceable condition.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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Task Associated Data

**CONF 001

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 002

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 003

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF 004

Zone

212

Manpower

TOTAL MANHOURS 11.50

ELAPSED TIME (HOURS) 11.50

**CONF ALL

A. GENERAL

**CONF 001

(1) Subtask 254351-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

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References

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 254351-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 002

(1) Subtask 254351-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

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(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 254351-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 003

(1) Subtask 254351-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

(2) Subtask 254351-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF 004

(1) Subtask 254351-910-003-001 - Standard Practices

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) 06-20-00, Page Block 001

06-41-52, Page Block 001

Structural Repair Manual (SRM) 51-24-00

51-42-00

51-43-00

51-44-00

51-75-12

(a) For the specification of the material (Mat. No.) given in this Service Bulletin, refer to

Consumable Materials (CML).

(b) For the identification of zones, refer to AMM 06-20-00, Page Block 001.

(c) For the identification of access panels, refer to AMM 06-41-52, Page Block 001.

(d) Remove and install fasteners in accordance with SRM 51-42-00.

(e) Obtain alternative and substitute fastener data, in accordance with SRM 51-43-00.

(f) Obtain fasteners hole diameters and drill and "deburr" data in accordance with

SRM 51-44-00.

(g) Cut the rivets to the necessary length.

(h) Renew the protective finish in accordance with SRM 51-75-12.

(i) Apply sealant in accordance with SRM 51-24-00.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 95

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(2) Subtask 254351-839-003-001 - Administrative

Manpower Resources

Skills NON SPECIFIC

Write in the applicable aircraft records that you have done all the work given in this

Service Bulletin.

**CONF ALL

B. PREPARATION

**CONF 001

(1) Subtask 254351-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

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(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 002

(1) Subtask 254351-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

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(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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**CONF 003

(1) Subtask 254351-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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(g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

(2) Subtask 254351-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

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3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF 004

(1) Subtask 254351-941-003-001 - Job Set-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 12-34-24-860-802

Task 25-11-51-000-801

Task 31-63-22-000-801

Task 33-12-13-000-801

Task 52-10-00-010-801

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) The following items shall be considered as the basic Aircraft configuration before

you start a maintenance task:

- Aircraft on the ground resting on landing gear (the ground safety locks and the

wheel chocks are in position on the landing gear).

- Engine shut down, thrust reversers closed and locked.

- Aircraft in clean configuration.

- Parking brake applied.

- Aircraft electrical network de-energized.

- Hydraulic systems depressurized.

- Access to the cockpit and cabin is available.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

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- All circuit breakers are in closed position.

- All controls in NORM, AUTO or OFF position.

(b) Make sure that the aircraft is electrically grounded, refer to AMM Task

12-34-24-860-802.

(c) Put the access platform in position door 831 or 841.

(d) Open the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) If necessary, remove the First Officer Seat (FIN 4MS), refer to AMM Task

25-11-51-000-801.

(f) Do the Job Set-up procedure as specified in the removal of the Display Unit

(DU)(FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

(g) In the cockpit, on the panel235VU, make sure that these pushbutton switches are

released:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(h) If necessary, remove the Light Unit (LU) (FIN 14LE), refer to AMM Task

33-12-13-000-801.

(i) Open, safety/lock and tag these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(j) Make sure that there are warning notices in the cockpit to tell persons not to

operate the pushbutton switches on the overhead panels:

- 211VU (EMER ELEC PWR)

- 235VU (ELEC)

(k) Make sure that there are warning notices in the cockpit to tell persons not to start

the APU.

(l) Make sure that the external connectors are not connected to the aircraft

receptacles EXT PWR A (B).

(m) Make sure that there is a warning notice at the access door 121EL to tell persons

not to connect the external power connectors.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 104

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@A340

SERVICE BULLETIN

(2) Subtask 254351-010-003-001 - Remove/Open for Access

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-000-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

NOTE: If you intend to accomplish this Repair Task during the same layover

period as the associated Inspection, the subsequent Preparation

procedure is not necessary.

(a) Remove the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retain

3 Washer Item (2) Retain

1 Panel Item (3) Retain

(b) Remove the cover assembly panel.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retain

1 Panel Item (4) Retain

(c) Remove the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-000-801.

**CONF ALL

C. PROCEDURE

**CONF 001

(1) Subtask 254351-833-002-001 - Replace the Bracket No. 7

Work Zones and Access Panels

Zone Access/Work location

212

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 105

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@A340

SERVICE BULLETIN

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA08

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

7 NAS6604-10 1 BOLT

8 NAS1726-4E 1 NUT

15 ASNA2050DEJ4020 4 RIVET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAA

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAA

In accordance with SRM 51-42-00

1 Remove:

1 Screw Item (7) Discard

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 106

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SERVICE BULLETIN

1 Nut Item (8) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAA

In accordance with SRM 51-42-00 and SRM 51-44-00.

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 7.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NAS6604-10 Item 7

NOTE: Install the bolt item 7 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBDAA Sheet 04

a Check that the minimum clearances are 0.35 mm (0.026 in) at LHS and

0.65 mm (0.014 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 107

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SERVICE BULLETIN

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 8:

1 Nut NAS1726-4E Item 8

NOTE: Torque the nut item 8 to a torque value between 0.28 and 0.37

mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 108

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SERVICE BULLETIN

**CONF 002

(1) Subtask 254351-833-002-002 - Replace the Bracket No. 7

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA09

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

20 MS24665-134 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAB

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 109

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SERVICE BULLETIN

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAB

In accordance with SRM 51-42-00

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (20) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAB

In accordance with SRM 51-42-00 and SRM 51-44-00

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 110

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SERVICE BULLETIN

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBDAB Sheet 04

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-134 Item 20

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 111

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SERVICE BULLETIN

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 003

(1) Subtask 254351-833-002-003 - Replace the Bracket No. 7

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA10

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 112

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SERVICE BULLETIN

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAC

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00 and SRM 51-44-00

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 113

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SERVICE BULLETIN

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBDAC Sheet 04.

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 114

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

**CONF 004

(1) Subtask 254351-833-002-004 - Replace the Bracket No. 7

Work Zones and Access Panels

Zone Access/Work location

212

Manpower Resources

Manhours 2.00

Minimum number of person 1

Subtask elapsed time 2.00

Skills NON SPECIFIC

Material necessary to do the job

Component COMPA01

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

16 F2511012820095 1 BRACKET

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 115

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SERVICE BULLETIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Component COMPA10

ITEM NEW PART N ̊ QTY (UM) KEYWORD SEE

NOTES

15 ASNA2050DEJ4020 4 RIVET

17 NSA5042-04-160 1 BOLT

18 NSA5060-3 1 NUT

19 NSA5325-3 1 WASHER

21 MS24665-71 1 PIN

NOTE: The above list of components is not an AIRBUS Kit, the required parts

shall be ordered as necessary through the given channel.

Consumable CMLA01

ITEM DESCRIPTION REFERENCE TO

CML MAT. No.

QTY PER A/C SEE

NOTES

Synthetic Ester Base

Grease-General Purpose

Low T

03HBD9 As required

References

Structural Repair Manual (SRM) 51-42-00

51-44-00

Fig. A-FBDAC

Replacement of the bracket No. 7

Sheet 01

Sheet 02

Sheet 03

Sheet 04

(a) Remove the bracket No. 7.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00

1 Remove:

1 Axis Item (17) Discard

1 Nut Item (18) Discard

1 Washer Item (19) Discard

1 Pin Item (21) Discard

2 Remove the rivets:

- Remove the head of the four rivets.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 116

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SERVICE BULLETIN

- Drill four holes through the cockpit main panel to remove the four rivets

and obtain a diameter comprised between 4.07 and 4.16 mm (0.160 and

0.164 in).

4 Rivet Item (15) Discard

3 Remove the bracket:

1 Bracket F2511012820000 Item (16) Discard

(b) Install the new bracket.

Refer to Fig. A-FBDAC

In accordance with SRM 51-42-00 and SRM 51-44-00

1 Temporarily put the new bracket item 16 on the RH side of the upper bracket.

a Mark the position of the hole of the upper bracket on the new bracket.

2 On bench, drill the marked hole to a diameter comprised between 6.5 and 6.7

mm (0.256 and 0.264 in).

3 Put in position the new bracket item 16 with the bolt item 17.

Install:

1 Bracket F2511012820095 Item 16

1 Bolt NSA5042-04-160 Item 17

NOTE: Install the bolt item 17 with:

Synthetic Ester

Base GreaseGeneral Purpose

Low T

03HBD9 As required

4 Measure the clearance between the new bracket item 16 and the upper

bracket as shown in Fig. A-FBDAC Sheet 04.

a Check that the minimum clearances are 0.35 mm (0.014 in) at LHS and

0.65 mm (0.026 in) at RHS.

5 Drill the four holes in the bracket item 16 to align with the holes of the

structure.

6 Install:

4 Rivet ASNA2050DEJ4020 Item 15

7 Install the nut item 18:

1 Nut NSA5060-3 Item 18

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 117

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SERVICE BULLETIN

1 Washer NSA5325-3 Item 19

1 Pin-Cotter MS24665-71 Item 21

NOTE: Torque the nut item 18 to a torque value between 0.28 and

0.37 mdaN (24.782 and 32.748 lbf.in).

(2) Subtask 254351-410-004-001 - Install/Close Items Removed/Opened for access

Manpower Resources

Manhours 0.50

Minimum number of person 1

Subtask elapsed time 0.50

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 31-63-22-400-801

Fig. A-FBCAA

Removal/Installation of the protection

plate and cover assembly panels

Sheet 01

Sheet 02

(a) Install the DU (FINs 1WK2 and 3WK2), refer to AMM Task 31-63-22-400-801.

(b) Install the cover assembly plate.

Refer to Fig. A-FBCAA Sheet 02

3 Stud Item (5) Retained at

removal

1 Panel Item (4) Retained at

removal

(c) Install the protection plate.

Refer to Fig. A-FBCAA Sheet 01

3 Stud Item (1) Retained at

removal

3 Washer Item (2) Retained at

removal

1 Panel Item (3) Retained at

removal

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 118

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SERVICE BULLETIN

**CONF ALL

D. TEST

**CONF 001

(1) Subtask 254351-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 119

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@A340

SERVICE BULLETIN

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

**CONF 002

(1) Subtask 254351-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 120

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SERVICE BULLETIN

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 121

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SERVICE BULLETIN

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

**CONF 003

(1) Subtask 254351-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 122

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SERVICE BULLETIN

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 123

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SERVICE BULLETIN

**CONF 004

(1) Subtask 254351-700-005-001 - Test

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 21-26-00-710-803

Task 22-96-00-740-801

Task 22-97-00-740-801

Task 24-41-00-861-801

Task 25-11-51-400-801

Task 31-50-00-710-803

Task 31-50-00-740-801

Task 31-60-00-710-802

Task 31-63-22-200-802

Task 33-12-13-400-801

Task 33-13-00-710-801

Task 33-14-00-710-801

Elec. Std. Practices Manual (ESPM) 20-52-20

NOTE: This test procedure is to be accomplished after the installation of the

equipment removed for access, refer to SUBTASK 254351-410-002 001

Install/Close Items Removed/Opened for access.

(a) In the cockpit, on the panel 235VU, push these pushbutton switches:

- BAT 1, BAT 2, APU BAT,

- GEN 1, (2), APU GEN,

- EXT A (B).

(b) Remove the warning notices.

(c) Energize the aircraft electrical circuits, refer to AMM Task 24-41-00-861-801.

(d) Remove the safety clips and/or tags and close/unlock these circuit breakers:

PANEL DESIGNATION FIN LOCATION SEE

NOTES

742 701PP 10PB1 72 S

742 702PP 10PB2 71 S

(e) Preliminary test:

NOTE: If the aircraft is operated in actual CAT III conditions, you must

also do the LAND CAT III capability test, refer to AMM Task

22-97-00-740-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 124

5

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SERVICE BULLETIN

1 On each connector which was disconnected:

- Do the checks as defined by ESPM 20-52-20.

NOTE: The functional test and/or operational test (OT) requested by

this ESPM procedure is given hereafter.

2 Do the OT of the instrument and Panel Integral Lighting, refer to AMM Task

33-13-00-710-801.

3 Do the OT of Lights, refer to AMM Task 33-14-00-710-801.

4 Do the OT of the Avionics-Equipment Ventilation System, refer to AMM Task

21-26-00-710-803.

5 Do the OT of the Auto Flight System (SYSTEM TEST), refer to AMM Task

22-96-00-740-801.

6 Do the OT of the ECAM Control Panel, refer to AMM Task 31-50-00-710-803.

7 Do the test of the FWS, AMM Task 31-50-00-740-801.

8 Do the OT of the EIS, refer to AMM Task 31-60-00-710-802.

(f) Do the test procedure as specified after the installation of the DU (FINs 1WK2 and

3WK2), refer to AMM Task 31-63-22-200-802.

(g) If removed, do the test procedure as specified after the installation of the First

Officer Seat (FIN 4MS ), refer to AMM Task 25-11-51-400-801.

(h) If removed, do the test procedure as specified after the installation of the LU (FIN

14LE ), refer to AMM Task 33-12-13-400-801.

**CONF ALL

E. CLOSE-UP

**CONF 001

(1) Subtask 254351-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

(a) Make sure that the work areas are clean and clear of tools and other items.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 125

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SERVICE BULLETIN

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

**CONF 002

(1) Subtask 254351-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 126

5

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@A340

SERVICE BULLETIN

**CONF 003

(1) Subtask 254351-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

**CONF 004

(1) Subtask 254351-942-003-001 - Close-up

Manpower Resources

Skills NON SPECIFIC

References

Aircraft Maintenance Manual (AMM) Task 25-11-51-400-801

Task 31-63-22-400-801

Task 33-12-13-400-801

Task 52-10-00-010-801

(a) Make sure that the work areas are clean and clear of tools and other items.

(b) Parts and/or equipment removed for access, to be installed before the SUBTASK

254351-700-003 001 Testing

1 Install the LU (FIN 14LE ), refer to AMM Task 31-63-22-400-801.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 127

5

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@A340

SERVICE BULLETIN

2 If removed, install the First Officer Seat (FIN 4MS ), refer to AMM Task

25-11-51-400-801.

(c) Do the close-up procedure as specified in the installation of DU (FINs 1WK2 and

3WK2), refer to AMM Task 33-12-13-400-801.

(d) Close the passenger/crew door 831 or 841, refer to AMM Task 52-10-00-010-801.

(e) Remove the access platform.

(f) Restore the systems and the aircraft to normal operation conditions.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 128

5

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SERVICE BULLETIN

**CONF ALL

BRACKET No 6

A

A

BRACKET No 7

C

B

F_SB_254351_5_BAAA_01_01

Figure A-FBAAA - Sheet 01

Area to be inspected

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 129

5

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@A340

SERVICE BULLETIN

**CONF ALL

TYPICAL CRACKS LOCATIONS

AREAS TO BE INSPECTED 

(BOTH SIDES OF THE TWO LUGS)

B C

TYPICAL CRACKS LOCATIONS

D

D

F_SB_254351_5_BAAA_02_02

Figure A-FBAAA - Sheet 02

Area to be inspected

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 130

5

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@A340

SERVICE BULLETIN

**CONF 001

BRACKET No 6

A

A

B C

F_SB_254351_5_BBAA_01_01

Figure A-FBBAA - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 131

5

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@A340

SERVICE BULLETIN

**CONF 001

(16)

FWD

BEFORE

(7)

(8)

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

RIVET

RIVET

ASNA2050DCJ3215 RIVET

(15)

(14)

(11)

ASNA2051DEJ4020

ASNA2050DEJ4020

F_SB_254351_5_BBAA_02_03

Figure A-FBBAA - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 132

5

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@A340

SERVICE BULLETIN

**CONF 001

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2050DCJ3215 RIVET

15

11

4.06 mm

(0.160 in)

4.17 mm

(0.164 in) ASNA2050DEJ4020

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

F_SB_254351_5_BBAA_03_05

Figure A-FBBAA - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 133

5

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@A340

SERVICE BULLETIN

**CONF 001

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 8 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

7

16

8

A A

01 01

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

F_SB_254351_5_BBAA_04_02

Figure A-FBBAA - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 134

5

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@A340

SERVICE BULLETIN

**CONF 002

BRACKET No 6

A

B C

A

F_SB_254351_5_BBAC_01_00

Figure A-FBBAC - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 135

5

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@A340

SERVICE BULLETIN

**CONF 002

(16)

FWD

BEFORE

(17)

(18)

B

(19)

(20)

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

RIVET

RIVET

ASNA2050DCJ3215 RIVET

(15)

(14)

(11)

ASNA2051DEJ4020

ASNA2050DEJ4020

F_SB_254351_5_BBAC_02_02

Figure A-FBBAC - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 136

5

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@A340

SERVICE BULLETIN

**CONF 002

16

FWD

AFTER

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2050DCJ3215 RIVET

15

11

4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

01

C

F_SB_254351_5_BBAC_03_04

Figure A-FBBAC - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 137

5

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@A340

SERVICE BULLETIN

**CONF 002

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

A A

01 01

16

17

19

18

20

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

F_SB_254351_5_BBAC_04_01

Figure A-FBBAC - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 138

5

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@A340

SERVICE BULLETIN

**CONF 003

BRACKET No 6

A

B C

A

F_SB_254351_5_BBAD_01_00

Figure A-FBBAD - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 139

5

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@A340

SERVICE BULLETIN

**CONF 003

(16)

FWD

BEFORE

(17)

(18)

B

(19)

(21)

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

RIVET

RIVET

ASNA2050DCJ3215 RIVET

(15)

(14)

(11)

ASNA2051DEJ4020

ASNA2050DEJ4020

F_SB_254351_5_BBAD_02_02

Figure A-FBBAD - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 140

5

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@A340

SERVICE BULLETIN

**CONF 003

16

FWD

AFTER

C

01

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

RIVET

ASNA2050DCJ3215 RIVET

15

11

4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

NOTE:

01 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

F_SB_254351_5_BBAD_03_03

Figure A-FBBAD - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 141

5

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@A340

SERVICE BULLETIN

**CONF 003

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

A A

01 01

16

17

19

18

21

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

F_SB_254351_5_BBAD_04_01

Figure A-FBBAD - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 142

5

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@A340

SERVICE BULLETIN

**CONF 004

BRACKET No 6

A

B C

A

F_SB_254351_5_BBAB_01_00

Figure A-FBBAB - Sheet 01

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 143

5

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SERVICE BULLETIN

**CONF 004

(6)

FWD

BEFORE

(17)

(18)

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

BOLT

ASNA2050DCJ3215 RIVET

(9)

(11)

EN6115V3−5

(10) ASNA2531−3 NUT

(19)

(21)

F_SB_254351_5_BBAB_02_04

Figure A-FBBAB - Sheet 02

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 144

5

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@A340

SERVICE BULLETIN

**CONF 004

6

FWD

AFTER

C

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

BOLT

ASNA2050DCJ3215 RIVET

9

11

4.780 mm

(0.189 in)

4.821 mm

(0.190 in)

EN6115V3−5

3.25 mm

(0.128 in)

3.35 mm

(0.132 in)

10 ASNA2531−3 NUT

NOTE:

01 DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

A

A

01

F_SB_254351_5_BBAB_03_03

Figure A-FBBAB - Sheet 03

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 145

5

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@A340

SERVICE BULLETIN

**CONF 004

NOTE:

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

01

TORQUE THE NUT ITEM 18 TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

02

A A

01 01

6

17

19

18

21

02

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

F_SB_254351_5_BBAB_04_02

Figure A-FBBAB - Sheet 04

Replacement of the bracket No. 6

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 146

5

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SERVICE BULLETIN

**CONF 001

A

BRACKET No 7

B C

A

F_SB_254351_5_BDAA_01_00

Figure A-FBDAA - Sheet 01

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 147

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@A340

SERVICE BULLETIN

**CONF 001

FWD

BEFORE

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

(15) ASNA2050DEJ4020 RIVET

(7)

(8)

(16)

F_SB_254351_5_BDAA_02_01

Figure A-FBDAA - Sheet 02

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 148

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@A340

SERVICE BULLETIN

**CONF 001

AFTER

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

15 RIVET 4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

16

FWD

NOTE:

01

01

A

A

C

F_SB_254351_5_BDAA_03_01

Figure A-FBDAA - Sheet 03

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 149

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SERVICE BULLETIN

**CONF 001

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

TORQUE THE NUT ITEM TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

7

16

8

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

A A

NOTE:

01

02

01

02

01

8

F_SB_254351_5_BDAA_04_00

Figure A-FBDAA - Sheet 04

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 150

5

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@A340

SERVICE BULLETIN

**CONF 002

A

BRACKET No 7

B C

A

F_SB_254351_5_BDAB_01_00

Figure A-FBDAB - Sheet 01

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 151

5

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@A340

SERVICE BULLETIN

**CONF 002

FWD

BEFORE

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

(15) ASNA2050DEJ4020 RIVET

(17)

(18)

(19)

(20)

(16)

F_SB_254351_5_BDAB_02_01

Figure A-FBDAB - Sheet 02

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 152

5

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SERVICE BULLETIN

**CONF 002

AFTER

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

15 RIVET 4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

16

FWD

NOTE:

01

01

A

A

C

F_SB_254351_5_BDAB_03_01

Figure A-FBDAB - Sheet 03

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 153

5

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@A340

SERVICE BULLETIN

**CONF 002

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

TORQUE THE NUT ITEM TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

17

16

18

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

A A

NOTE:

01

02

01

02

01

18

20

19

F_SB_254351_5_BDAB_04_00

Figure A-FBDAB - Sheet 04

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 154

5

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@A340

SERVICE BULLETIN

**CONF 003 thru 004

A

BRACKET No 7

B C

A

F_SB_254351_5_BDAC_01_00

Figure A-FBDAC - Sheet 01

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 155

5

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@A340

SERVICE BULLETIN

**CONF 003 thru 004

FWD

BEFORE

B

HOLE

SYMBOL ITEM OLD PN DESCRIPTION

(15) ASNA2050DEJ4020 RIVET

(16)

(17)

(18)

(19)

(21)

F_SB_254351_5_BDAC_02_01

Figure A-FBDAC - Sheet 02

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 156

5

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@A340

SERVICE BULLETIN

**CONF 003 thru 004

AFTER

HOLE

SYMBOL ITEM PN DESCRIPTION

HOLE DIAMETER

MIN MAX

15 RIVET 4.07 mm

(0.160 in)

4.16 mm

(0.164 in) ASNA2050DEJ4020

DRILL THE MARKED HOLE TO DIAMATER COMPRISED BETWEEN 6.5 mm (0.256 in)

AND 6.7 mm (0.264 in) 

16

FWD

NOTE:

01

01

A

A

C

F_SB_254351_5_BDAC_03_01

Figure A-FBDAC - Sheet 03

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 157

5

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@A340

SERVICE BULLETIN

**CONF 003 thru 004

CHECK THAT THE MINIMUM CLEARANCES ARE 0.35 mm (0.014 in) AT LHS

AND 0.65 mm (0.026 in) AT RHS

TORQUE THE NUT ITEM TO A TORQUE VALUE BETWEEN 0.28 m.daN (24.782 lbf.in)

AND 0.37 m.daN (32.748 lbf.in)

17

16

18

MEASURE THE

CLEARANCE

MEASURE THE

CLEARANCE

A A

NOTE:

01

02

01

02

01

18

21

19

F_SB_254351_5_BDAC_04_00

Figure A-FBDAC - Sheet 04

Replacement of the bracket No. 7

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 158

5

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SERVICE BULLETIN

**CONF ALL

(3)

(1)

(2)

A

A B

F_SB_254351_5_BCAA_01_00

Figure A-FBCAA - Sheet 01

Removal/Installation of the protection plate and cover assembly panels

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 159

5

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SERVICE BULLETIN

**CONF ALL

(4)

(5)

TYPICAL INSTALATION

C C

C

C

B

F_SB_254351_5_BCAA_02_00

Figure A-FBCAA - Sheet 02

Removal/Installation of the protection plate and cover assembly panels

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 160

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SERVICE BULLETIN

**CONF ALL

QUESTION

ACTION

FINDING

YES CRACKS FOUND

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

REFER TO TASK 254351−832−801−001

BRACKET LUGS ARE

FULLY BROKEN YES

DO A DETAILED INSPECTION OF THE COCKPIT

INSTRUMENT PANEL BRACKET No 7

OR

YES CRACKS FOUND?

CONTACT AIRBUS

BEFORE NEXT

FLIGHT

REPLACE BRACKET No 6 AND BRACKET No 7

REFER TO TASK 254351−833−801−001

REFER TO SUBTASK 254351−700−004−001

TWO

BEFORE NEXT FLIGHT

NO

REPLACE BRACKET No 6

REFER TO TASK 254351−833−801−001

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

DO A DETAILED INSPECTION OF THE COCKPIT

INSTRUMENT PANEL BRACKET No 6

REFER TO TASK 254351−832−801−001

AT THE INTERVAL GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

NO

NO

INSTRUMENT PANEL BRACKET No 6

DO A DETAILED INSPECTION OF THE COCKPIT

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

REFER TO TASK 254351−832−801−001

INSTRUMENT PANEL BRACKET No 6

DO A DETAILED INSPECTION OF THE COCKPIT

NOTE:

THE PURPOSE OF FLOW CHARTS IS TO SUPPLEMENT THE INFORMATION GIVEN IN THE PROCEDURE

AND COMPLIANCE PARAGRAPHS AND NOT TO SERVE AS THE PRIMARY SOURCE FOR TASKS OR

COMPLIANCE TIMES GIVEN IN THIS SERVICE BULLETIN.

AT THE THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

AND TASK 254351−833−802−001

REPLACE BRACKET No 7

REFER TO TASK 254351−833−802−001

BEFORE NEXT FLIGHT

OR

OR

IMPLEMENT SB No 25−4354

AS TERMINATIVE SOLUTION

IMPLEMENT SB No 25−4354 AS

TERMINATIVE SOLUTION AT THE

THRESHOLD GIVEN IN THE PLANNING

INFORMATION PARAGRAPH E.(2)

F_SB_254351_5_FAAA_01_08

Figure A-FFAAA - Sheet 01

Flow-chart

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 161

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SERVICE BULLETIN

**CONF ALL

INSPECTION REPORT

RETURN TO: 

AIRBUS

CUSTOMER SERVICES ENGINEERING − SEES1

FUSELAGE (WB/LR) − VERTICAL TAIL PLANE − CENTER

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX

FRANCE

E−mail: Structure.sbinspectionresult@airbus.com

FAX +33 (0)5 61 93 36 14

WING BOX (WB/LR)

SERVICE BULLETIN NO.:

A/C MSN:

OPERATOR:

FLIGHT HOURS (FH):

FLIGHT CYCLES (FC):

INSPECTION METHOD:

DATE OF INSPECTION:

A340−25−4351

DETAILED

INSPECTION

CRACKS FOUND YES NO

TWO LUGS FULLY BROKEN YES NO

BRACKET REPLACED YES NO

CRACKS FOUND YES NO

BRACKET NUMBER 6

BRACKET NUMBER 7

BRACKET REPLACED YES NO

F_SB_254351_5_RAAA_01_01

Figure A-FRAAA - Sheet 01

Inspection Report

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 162

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SERVICE BULLETIN

REPORTING SHEET

TITLE: EQUIPMENT/FURNISHINGS - COCKPIT - INSPECTION OF COCKPIT

INSTRUMENT PANEL BRACKET 6.

MODIFICATION No.: None

Please complete the appropriate item (A or B):

A - SB WILL BE embodied YES/NO (if NO please comment)

If YES, aircraft concerned (as per SB effectivity by default) and planned dates (month/year) of

embodiment:

B - SB HAS BEEN embodied on aircraft:

Operator comments:

From Airline:

Name/Title:

Signature: Date:

If operational documentation is affected (see Paragraph 1.K of this SB): If information is needed prior to

next normal revision or prior to SB embodiment, please indicate required service(s):

Either: Modification Operational Impact (MOI), if available YES/NO

Or : Intermediate revision YES/NO

Important Information: This SB will only be incorporated in your maintenance and operational

documentation if this sheet is returned to Airbus and signed by a duly authorised representative. With

the next feasible revision, this will result in

- Updating of maintenance documentation to show pre and post SB data.

- Updating of maintenance and operational documentation to show post SB data after embodiment.

If this SB requires previous or simultaneous accomplishment of other SBs, Airbus shall automatically

include them in the manual revisions. Refer to SIL 00-037 for detailed information.

Please return this completed sheet to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn: SDC32 Technical Data and Documentation Services

FAX: (+33) 5 61 93 28 06

e-mail: sb.reporting@airbus.com

or via your Resident Customer Support Office.

Alternatively, SB lists via letters or fax are also accepted.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 1

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SERVICE BULLETIN

QUALITY PERCEPTION FORM

Use this form to tell us what is your perception of the quality of this Service Bulletin. The reported data

that you provide us will be used to analyse areas of difficulties and to take corrective action to further

improve the quality of our Service Bulletins.

We thank you for the time you have taken in completing this form.

(Please rate on a scale of 1 to 4, with 4 being the highest score)

- Quality rating of this SB 4321

- Quality rating of the Accomplishment Instructions 4321

- Quality rating of the Illustrations 4321

- Is this SB easy to understand ? Y/N

If you have had difficulties in the accomplishment of this SB please quote below the area(s) and give a

short description of the issue.

Planning Material Instructions

X Effectivity X Kit content X Preparation

X Reason X List of Materials Operator Supplied X Mod/Inspection

X Manpower X Industry support X Test

X References X Re-identification X Close-Up

X Publication X Tooling X Illustrations

Comments:

Operator: Date:

Name/Title:

Please return this form to:

AIRBUS

CUSTOMER SERVICES DIRECTORATE

1 Rond Point Maurice Bellonte

31707 BLAGNAC CEDEX FRANCE

Attn : SEM4 Service Bulletins Management

FAX : (33) 5 61 93 42 51

Or via your Resident Customer Support Office.

DATE: Sep 10/13 SERVICE BULLETIN No.: A340-25-4351

REVISION No.: 01 - Jan 31/14 Page: 1

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